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AG36 (ag36-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: AG36 (ag36-il)
Reynolds number: 500,000
Max Cl/Cd: 81.02 at α=3.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ag36-il-500000-n5.txt
Download as CSV file: xf-ag36-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: AG36                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5459   0.08727   0.08505  -0.0058   1.0000   0.0082
 -10.000  -0.5493   0.08189   0.07970  -0.0094   1.0000   0.0082
  -9.750  -0.5545   0.07615   0.07400  -0.0142   1.0000   0.0082
  -9.500  -0.5551   0.06809   0.06593  -0.0237   1.0000   0.0082
  -9.250  -0.5549   0.05722   0.05496  -0.0346   1.0000   0.0083
  -9.000  -0.5968   0.02470   0.02065  -0.0457   1.0000   0.0086
  -8.750  -0.5790   0.02165   0.01709  -0.0449   1.0000   0.0088
  -8.500  -0.5595   0.01946   0.01453  -0.0441   1.0000   0.0092
  -8.250  -0.5373   0.01856   0.01353  -0.0433   1.0000   0.0095
  -8.000  -0.5146   0.01780   0.01266  -0.0425   1.0000   0.0099
  -7.750  -0.4871   0.01681   0.01150  -0.0427   0.9982   0.0103
  -7.500  -0.4545   0.01561   0.01008  -0.0439   0.9949   0.0107
  -7.250  -0.4225   0.01457   0.00884  -0.0449   0.9906   0.0112
  -7.000  -0.3904   0.01369   0.00780  -0.0458   0.9857   0.0118
  -6.750  -0.3585   0.01298   0.00697  -0.0467   0.9802   0.0122
  -6.500  -0.3275   0.01213   0.00600  -0.0474   0.9735   0.0128
  -6.250  -0.2963   0.01161   0.00545  -0.0481   0.9663   0.0136
  -6.000  -0.2652   0.01125   0.00505  -0.0487   0.9573   0.0148
  -5.750  -0.2357   0.01085   0.00459  -0.0489   0.9464   0.0159
  -5.500  -0.2069   0.01048   0.00413  -0.0489   0.9330   0.0167
  -5.250  -0.1796   0.00999   0.00358  -0.0487   0.9171   0.0182
  -5.000  -0.1528   0.00972   0.00325  -0.0482   0.8971   0.0198
  -4.750  -0.1266   0.00952   0.00293  -0.0475   0.8716   0.0218
  -4.500  -0.1003   0.00929   0.00262  -0.0469   0.8512   0.0252
  -4.250  -0.0735   0.00914   0.00238  -0.0465   0.8322   0.0290
  -4.000  -0.0464   0.00898   0.00215  -0.0461   0.8152   0.0350
  -3.750  -0.0193   0.00883   0.00196  -0.0459   0.7979   0.0466
  -3.500   0.0080   0.00869   0.00180  -0.0456   0.7788   0.0650
  -3.250   0.0352   0.00850   0.00166  -0.0454   0.7587   0.0982
  -2.750   0.0895   0.00806   0.00143  -0.0452   0.7155   0.2121
  -2.500   0.1164   0.00784   0.00136  -0.0451   0.6825   0.2920
  -2.250   0.1426   0.00768   0.00128  -0.0448   0.6319   0.3790
  -2.000   0.1689   0.00745   0.00124  -0.0447   0.6039   0.4881
  -1.750   0.1946   0.00708   0.00125  -0.0444   0.5852   0.6344
  -1.500   0.2179   0.00666   0.00129  -0.0433   0.5709   0.7901
  -1.250   0.2392   0.00641   0.00134  -0.0412   0.5589   0.9231
  -1.000   0.2805   0.00644   0.00132  -0.0440   0.5460   0.9907
  -0.750   0.3115   0.00654   0.00132  -0.0446   0.5348   1.0000
  -0.500   0.3388   0.00663   0.00134  -0.0445   0.5239   1.0000
  -0.250   0.3663   0.00672   0.00137  -0.0444   0.5131   1.0000
   0.000   0.3938   0.00682   0.00140  -0.0443   0.5022   1.0000
   0.250   0.4213   0.00693   0.00144  -0.0442   0.4905   1.0000
   0.500   0.4488   0.00704   0.00149  -0.0442   0.4781   1.0000
   0.750   0.4765   0.00714   0.00154  -0.0442   0.4640   1.0000
   1.000   0.5041   0.00725   0.00160  -0.0441   0.4477   1.0000
   1.250   0.5315   0.00739   0.00167  -0.0441   0.4292   1.0000
   1.500   0.5588   0.00755   0.00176  -0.0441   0.4091   1.0000
   1.750   0.5861   0.00773   0.00186  -0.0440   0.3881   1.0000
   2.000   0.6131   0.00795   0.00198  -0.0440   0.3648   1.0000
   2.250   0.6401   0.00817   0.00212  -0.0439   0.3414   1.0000
   2.500   0.6670   0.00842   0.00229  -0.0439   0.3200   1.0000
   2.750   0.6939   0.00866   0.00246  -0.0439   0.2978   1.0000
   3.000   0.7207   0.00894   0.00266  -0.0438   0.2757   1.0000
   3.250   0.7472   0.00924   0.00288  -0.0438   0.2513   1.0000
   3.500   0.7737   0.00955   0.00311  -0.0437   0.2269   1.0000
   3.750   0.8000   0.00988   0.00336  -0.0437   0.2048   1.0000
   4.000   0.8262   0.01024   0.00363  -0.0436   0.1817   1.0000
   4.250   0.8520   0.01064   0.00394  -0.0435   0.1569   1.0000
   4.500   0.8776   0.01108   0.00428  -0.0434   0.1322   1.0000
   5.000   0.9286   0.01194   0.00498  -0.0431   0.0938   1.0000
   5.250   0.9536   0.01242   0.00540  -0.0430   0.0752   1.0000
   5.500   0.9784   0.01293   0.00583  -0.0428   0.0582   1.0000
   5.750   1.0028   0.01348   0.00632  -0.0425   0.0427   1.0000
   6.000   1.0268   0.01407   0.00685  -0.0423   0.0305   1.0000
   6.250   1.0509   0.01465   0.00741  -0.0420   0.0223   1.0000
   6.500   1.0749   0.01521   0.00799  -0.0416   0.0175   1.0000
   6.750   1.0989   0.01575   0.00858  -0.0413   0.0147   1.0000
   7.000   1.1219   0.01642   0.00928  -0.0409   0.0123   1.0000
   7.250   1.1454   0.01698   0.00992  -0.0405   0.0108   1.0000
   7.500   1.1682   0.01761   0.01061  -0.0401   0.0095   1.0000
   7.750   1.1898   0.01839   0.01146  -0.0395   0.0085   1.0000
   8.000   1.2118   0.01907   0.01224  -0.0389   0.0079   1.0000
   8.250   1.2331   0.01982   0.01308  -0.0383   0.0073   1.0000
   8.500   1.2536   0.02061   0.01396  -0.0377   0.0068   1.0000
   8.750   1.2729   0.02151   0.01494  -0.0369   0.0064   1.0000
   9.000   1.2890   0.02272   0.01628  -0.0357   0.0060   1.0000
   9.250   1.3060   0.02375   0.01743  -0.0346   0.0058   1.0000
   9.500   1.3220   0.02481   0.01862  -0.0335   0.0057   1.0000
   9.750   1.3363   0.02598   0.01992  -0.0322   0.0055   1.0000
  10.000   1.3486   0.02724   0.02131  -0.0306   0.0053   1.0000
  10.250   1.3586   0.02858   0.02279  -0.0289   0.0051   1.0000
  10.500   1.3637   0.02997   0.02432  -0.0265   0.0050   1.0000
  10.750   1.3672   0.03154   0.02603  -0.0243   0.0049   1.0000
  11.000   1.3693   0.03334   0.02798  -0.0225   0.0048   1.0000
  11.250   1.3706   0.03538   0.03016  -0.0211   0.0047   1.0000
  11.500   1.3711   0.03771   0.03263  -0.0203   0.0046   1.0000
  11.750   1.3703   0.04041   0.03548  -0.0201   0.0045   1.0000
  12.000   1.3682   0.04352   0.03873  -0.0204   0.0044   1.0000
  12.250   1.3647   0.04709   0.04244  -0.0213   0.0044   1.0000
  12.500   1.3590   0.05125   0.04676  -0.0228   0.0043   1.0000
  12.750   1.3514   0.05605   0.05171  -0.0250   0.0043   1.0000
  13.000   1.3415   0.06135   0.05717  -0.0274   0.0042   1.0000
  13.250   1.3292   0.06712   0.06309  -0.0301   0.0042   1.0000
  13.500   1.3149   0.07329   0.06941  -0.0329   0.0042   1.0000
  13.750   1.2989   0.07989   0.07616  -0.0360   0.0042   1.0000
  14.000   1.2821   0.08681   0.08322  -0.0392   0.0042   1.0000
  14.250   1.2648   0.09407   0.09062  -0.0427   0.0042   1.0000
  14.500   1.2466   0.10176   0.09844  -0.0463   0.0042   1.0000
  14.750   1.2289   0.10956   0.10637  -0.0501   0.0042   1.0000
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